EP2216600B1 - Buse de brûleur - Google Patents
Buse de brûleur Download PDFInfo
- Publication number
- EP2216600B1 EP2216600B1 EP09004288.8A EP09004288A EP2216600B1 EP 2216600 B1 EP2216600 B1 EP 2216600B1 EP 09004288 A EP09004288 A EP 09004288A EP 2216600 B1 EP2216600 B1 EP 2216600B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- nozzle
- fuel
- tube
- flange
- primary
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000000446 fuel Substances 0.000 claims description 102
- 238000004891 communication Methods 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 description 44
- 238000012546 transfer Methods 0.000 description 13
- 238000009792 diffusion process Methods 0.000 description 8
- 238000011144 upstream manufacturing Methods 0.000 description 7
- 239000000203 mixture Substances 0.000 description 6
- 238000001816 cooling Methods 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- VEMKTZHHVJILDY-UHFFFAOYSA-N resmethrin Chemical compound CC1(C)C(C=C(C)C)C1C(=O)OCC1=COC(CC=2C=CC=CC=2)=C1 VEMKTZHHVJILDY-UHFFFAOYSA-N 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/48—Nozzles
- F23D14/58—Nozzles characterised by the shape or arrangement of the outlet or outlets from the nozzle, e.g. of annular configuration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/62—Mixing devices; Mixing tubes
- F23D14/64—Mixing devices; Mixing tubes with injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/46—Details, e.g. noise reduction means
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/76—Protecting flame and burner parts
Definitions
- the present invention relates to combustors that may be used in combustion turbines. More specifically, the present invention relates to a nozzle system for injecting fuel into a combustor.
- Gas turbines play a predominant role in a number of applications, namely in aircraft propulsion, marine propulsion, power generation and driving processes, such as pumps and compressors.
- a gas turbine includes a compressor, a combustor and a turbine.
- air is fed into the system where it is compressed by a compressor and a portion of the air further mixed with fuel.
- the compressed air and fuel mixture are then burned to cause an expansion, which is responsible for driving the turbine.
- combustors In an effort to reduce emissions, combustors have been designed to premix fuel and air prior to ignition. Premixed fuel and air burn at a lower temperature than the stoichiometric combustion, which occurs during traditional diffusion combustion. As a result, premixed combustion results in lower NOx emissions.
- a typical combustor includes a plurality of primary fuel nozzles that surround a central secondary nozzle.
- Traditional secondary nozzles may include passageways for diffusion fuel and premix fuel all within the same elongated tubular structure.
- This type of nozzle often includes a complex structure of passageways contained within a single tubular shell.
- the passageways for creating the diffusion flame extend through the length of the nozzle.
- Premix fuel is dispensed upstream of the diffusion tip in order to allow fuel to mix with compressed air flowing through the combustor prior to reaching the flame zone, which is located downstream of the nozzle.
- passageways for premix fuel are typically shorter than passageways for diffusion fuel.
- premix fuel may be mixed with air upstream of the diffusion tip and, more importantly, radially outward of the secondary nozzle structure.
- premix fuel is carried along only a portion of the nozzle length until it is passed radially outward from the nozzle body to a premix injector tip.
- the premix fuel is dispensed into the air flow path.
- the fuel and air continue to travel downstream along the remainder of the secondary nozzle length, they become mixed, allowing for more efficient combustion within the flame zone, downstream of the nozzle tip.
- EP 0 526 152 A1 is directed to reducing emission of Nox, CO and unburned hydrocarbons using premixing combustor tubes to premix fuel and air before the mixture is burned in a single combustion chamber.
- the tubes are flashback resistant due to the flow of the fuel and air mixture through them. If it is desired to reduce the load operation of the combustor to substantially below 100% of its maximum load operation, as is the case during off-peak hours, the fuel and air flow rate can be regulated to reduce the load operation while still keeping the low emissions and the low flame temperature.
- US 2006/026966 A1 is directed to a pilot nozzle support system for support a pilot nozzle in a fuel injection system of a turbine engine.
- the support system is configured to support the pilot nozzle with a sleeve and to increase the natural frequency of the pilot nozzle outside an excitation range to avoid destructive vibrations.
- the support system includes a sleeve that maintains contact with a support housing at substantially all times of operation of a turbine engine. Should the sleeve ever lose contact with the support housing during operation of a turbine engine, an insulative film of air may form between the sleeve and the support housing causing the sleeve to increase in temperature relative to the support housing. The sleeve, as a result, expands and regains contact with the support housing.
- a device comprising a secondary nozzle for inclusion within a combustor for a combustion turbine according to claim 1.
- the secondary nozzle comprises a flange and an elongated nozzle body extending from the flange.
- At least one premix fuel injector is spaced radially from the nozzle body and extends axially from the flange, generally parallel to the nozzle body.
- the secondary nozzle comprises a fuel source, a flange and a first nozzle tube extending axially from the flange. At least one second nozzle tube is spaced radially outward from the first nozzle tube and has a proximal end fixed to the flange. The second nozzle tube is fluidly connected to the fuel source. The second nozzle tube has a distal end, axially spaced from the proximal end of the second nozzle and having at least one aperture therein. A passageway extends between the proximal end of the second nozzle tube and the distal end of the second nozzle tube, said passageway fluidly connects the fuel source and the at least one aperture.
- Described herein is an exemplary combustor for use in a combustion turbine.
- the combustor of the type illustrated is one of a plurality of combustors, typically positioned after the compressor stage within the combustion turbine.
- the combustor is designated by the numeral 10 and as illustrated is a dual stage, dual mode combustor having a combustor flow sleeve 12, a rear wall assembly 14 and a combustor wall 13. Radially inward of the combustor wall 13 are provided a plurality of primary fuel nozzles 16 and a secondary fuel nozzle 18. The nozzles 16, 18 serve to inject fuel into the combustor 10.
- Inlet air for combustion is pressurized by the turbine compressor (not shown) and then directed into the combustor 10 via the combustor flow sleeve 12 and a transition duct (not shown). Air flow into the combustor 10 is used for both combustion and to cool the combustor 10. The air flows in the direction "A" between the combustor flow sleeve 12 and the combustor wall 13. Generally, the airflow illustrated is referred to as reverse flow because the direction "A" is in an upstream direction to the normal flow of air through the turbine and the combustion chambers.
- the combustor 10 includes a primary combustion chamber 42 and a secondary combustion chamber 44, located downstream of the primary combustion chamber 42.
- a venturi throat region 46 is located between the primary and secondary combustion chambers 42, 44.
- the primary nozzles 16 are arranged in an annular ring around the secondary nozzle 18.
- a centerbody 38 is defined by a liner 40 in the center of the combustor 10.
- each of the primary nozzles 16 are mounted on a rear wall assembly 14.
- the primary nozzles 16 protrude from the rear wall 14 and provide fuel to the primary combustion chamber 42.
- Fuel is delivered to the primary nozzles 16 via a primary fuel source 20.
- Spark or flame for combustion ignition in the primary combustion chamber 42 is typically provided by spark plugs or cross fire tubes (not shown).
- Air swirlers may be provided in connection with the primary nozzles 16 to facilitate mixing of combustion air with fuel to provide an ignitable mixture of fuel and air.
- combustion air is derived from the compressor and routed in the direction "A," between the combustor flow sleeve 12 and the combustor wall 13.
- the pressurized air flows radially inward between the combustor wall 13 and the rear wall 14 into the primary combustion chamber 42.
- the combustor wall 13 may be provided with slots or louvers (not shown) in both the primary and secondary combustion chambers 42, 44 for cooling purposes.
- the slots or louvers may also provide dilution air into the combustor 10 to moderate flame temperature within the primary or secondary combustion chambers 42, 44.
- the secondary nozzle 18 extends from a flange 22 into the combustor 10 through the rear wall 14.
- the secondary nozzle 18 extends to a point upstream of the venturi throat region 46 to introduce fuel into the secondary combustion chamber 44.
- the flange 22 may be provided with means for mounting (not shown) the secondary nozzle 18 on the rear wall 14 of the combustor 10.
- the mounting means may be a mechanical linkage, such as bolts, which serve to fix the flange 22 to the rear wall 14 and which facilitate the removal of the nozzle 18, such as for repairs or replacement. Other means for attachment are also contemplated.
- Fuel for the primary nozzles 16 is supplied by a primary fuel source 20 and is directed through the rear wall 14. Secondary transfer and premix fuel sources 24, 25 are provided through the flange 22 to the secondary nozzle 18. Although not shown here, the secondary nozzle 18 may also have a diffusion circuit or pilot circuit for injecting fuel into the combustor 10.
- the secondary nozzle 18 comprises a nozzle body 30 and at least one premix fuel injector 32.
- the secondary nozzle 18 is located within the centerbody 38 and is surrounded by the liner 40, as shown in Fig. 1 .
- the premix fuel injectors 32 are arranged on the flange 22 in a generally annular configuration, around the nozzle body 30, as best seen in Fig. 3 .
- Each of the premix fuel injectors 32 has a generally oblong or elongated cross-sectional shape when viewed from the top.
- a first side or end 34 of the injectors 32 is disposed proximate the nozzle body 30.
- a second side or end 36 of the injectors 32 is disposed radially outward of the first end 34.
- the premix fuel injectors 32 are shown aligned directly between the primary nozzles 16 and the nozzle body 30 to facilitate airflow through the centerbody 38 and around the nozzle body 30. In such an arrangement, the second ends 36 of the premix fuel injectors 32 are disposed proximate the primary nozzles 16.
- Air flow "A" into the combustor 10 travels radially inward from outside of the combustor wall 13. A portion of this air travels downstream, into and through the primary combustion chamber 42. Another portion of the air, by way of example 5 to 20% of the total air flow through the combustor, travels radially inward past the primary nozzles 16 and the primary combustion chamber 42 into the centerbody 38 before travelling downstream through the centerbody.
- premix fuel injectors 32 aligning the premix fuel injectors 32 radially inward of the primary nozzles 16, between the primary nozzles 16 and the secondary nozzle 18, allows for maximum airflow into the centerbody 38.
- premix fuel injectors 32 shown have an elongated cross section, other shapes may also be used, such as round, rectangular, triangular, etc.
- the secondary nozzle 18 is shown including a nozzle body 30 and premix fuel injectors 32. As described above, the secondary nozzle 18 is located in the centerbody 38 and surrounded by the liner 40 ( Fig. 1 ). The nozzle body 30 extends along the longitudinal axis of the centerbody 38. The nozzle body 30 has a generally elongated cylindrical outer sleeve portion 52 which defines a cavity 31 therein. As shown, transfer fuel passages 64 are located within the outer portion of cavity 31. The transfer fuel passages 64 extend distally from the flange 22 and are arranged at spaced locations in an annular configuration. Transferless variants are known and may also be utilized.
- the transfer fuel passages 64 are fluidly connected to the transfer manifold 51, which is fed by the transfer fuel source 24.
- the transfer fuel passages 64 include a longitudinal tube 66 and at least one radial passageway 68.
- the passageway 68 is directed radially outward from the tube 66 and is aligned with an aperture 71 in the wall of the nozzle body 30.
- the passageway 68 jets the fuel through the opening 71 to the outside of the sleeve 52 to mix with the air flowing along the wall 52.
- a second opening 70 is shown upstream of opening 71 and provides an inlet for air into the portion of the cavity 31 surrounding the central tube positioned within the nozzle body 30. A portion of the air moving past the opening 70 is directed into the cavity 31 to cool the nozzle body 30.
- the air in the cavity 31 is exhausted from the openings 58 on the end 54 of the nozzle.
- the central tube feeds fuel to the nozzle end 54 for supporting a flame in the secondary combustion chamber 44.
- the openings 70 are separated from the fuel provided by passageway 68 and the additional fuel provided by injectors 32. It is noted that additional openings may be provided to mix the flow of fuel outside the nozzle body 30 or to direct the flow of air into the nozzle cavity 31. Also, the fuel passages 64 may be eliminated if desired.
- the outer sleeve portion 52 of the nozzle body 30 extends from the flange 22 to a distal tip 54.
- the tip 54 of the nozzle body 30 has at least one aperture 58 for allowing the passage of pressurized air from inside of the passageway 31 that surrounds the central tube portion.
- the transfer fuel source 24 extends into the flange 22, providing fuel to the transfer manifold 51, which is fluidly connected to the transfer fuel passages 64.
- the premix fuel source 25 extends into the flange 22 and is in fluid communication with premix manifold chamber 50, which is fluidly connected to the premix fuel injectors 32.
- the premix fuel injectors 32 extend distally from the flange 22 having a length that is less than that of the nozzle body 30.
- a distal end 60 of the premix fuel injectors 32 includes premix apertures 62 for dispensing fuel into the area of the centerbody 38 outside of the nozzle body 30.
- the premix fuel is mixed with air flowing within the liner 40. When the mixture reaches the secondary combustion chamber 44, the mixture is optimized for efficient combustion in the secondary combustion chamber 44 (see Fig. 1 ).
- premix fuel injector 32 allows for a simplification of the nozzle body 30.
- the injectors 32 shown allow for less internal passageways inside the nozzle body 30 than the typical nozzles. This simplification reduces the stress on the secondary nozzle 18 that may arise from heat differentials within the nozzle structures 18, 32 due to the variation in temperature of the fuel and the pressurized air. Additionally, the contemplated design is easier to maintain and allows for a degree of modularity not possible with traditional secondary nozzles.
- premix fuel injectors 32 may have a dispensing ring fluidly connected to one or more sets of the premix apertures 62.
- Other dispenser tip structures may also be used with the premix fuel injectors 32 of the type particularly shown.
- flame 72 is first established in primary combustion chamber 42, upstream of secondary combustion chamber 44.
- the fuel for this initial flame is provided solely through the primary nozzles 16.
- a flame 72 is established in the secondary combustion chamber 44, while flame 72 also remains in the primary combustion chamber 42.
- a portion of the fuel is injected through the secondary nozzle 18, while a majority of the fuel is sent through the primary nozzles 16.
- 30% of the total fuel discharge is injected through the secondary nozzle while 70% of the fuel is sent through the primary nozzles 16. This flame pattern is indicative of a "lean-lean" type operation.
- Fig. 10 the entire fuel flow is directed through the nozzle body 30 of the secondary nozzle 18, establishing a stable flame within the secondary combustion chamber 44.
- the flame is extinguished in primary combustion chamber 42 by cutting off fuel flow to the primary nozzles 16.
- the fuel that was previously injected through the primary nozzles 16 is diverted to the secondary nozzle 18 through the transfer fuel passages 64.
- the transfer and premix fuel is injected upstream of the flame 72.
- the fuel and air flow through the secondary nozzle 18 is considered to be relatively "rich” at this stage because 100% of the fuel flows through the secondary nozzle 18 with only a portion of the air intended for combustion.
- a stable flame is established in the secondary combustion chamber 44 and the flame is extinguished in the primary combustion chamber 42, fuel flow may be restored to the primary nozzles 16 and the fuel flow to the secondary nozzle 18 is reduced. Because the flame has been extinguished from the primary combustion chamber 42, the primary nozzles 16 act as a premixer. During this "premix" operation mode, the flame is maintained in the secondary combustion chamber 44 as a result of the venturi throat region 46. By way of example, 83% of the total fuel discharge may be sent through the primary nozzles 16, while the remaining 17% of fuel is injected through the secondary nozzle 18. Other relative percentages are also possible.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Gas Burners (AREA)
- Spray-Type Burners (AREA)
Claims (10)
- Dispositif destiné à être utilisé dans un brûleur de turbine à gaz (10), le dispositif comprenant :des buses primaires (16) ; etune buse secondaire (18) comprenant :- une bride (22) ;- un corps de buse allongé (30) s'étendant depuis la bride (22) ; et- une pluralité d'injecteurs de carburant de prémélange (32) espacés radialement du corps de buse (30), les injecteurs (32) s'étendant axialement depuis la bride (22) et étant généralement parallèles au corps de buse (30) sur une partie de la longueur du corps de buse (30), dans lequel la pluralité d'injecteurs de carburant de prémélange (32) sont agencés en un réseau annulaire autour du corps de buse (30),dans lequel les buses primaires (16) sont agencées en un réseau circulaire autour de la buse secondaire (18) et les injecteurs de carburant de prémélange (32) sont disposés entre le corps de buse (30) et les buses primaires (16),caractérisé en ce qu'il y a un nombre identique d'injecteurs de carburant de prémélange (32) et de buses primaires (16).
- Dispositif selon la revendication 1, dans laquelle le corps de buse (30) mesure une première longueur et l'injecteur de carburant de prémélange (32) mesure une seconde longueur qui est inférieure à la première longueur.
- Dispositif selon la revendication 1 ou 2, dans lequel le dispositif est disposé à l'intérieur du brûleur (10) .
- Dispositif selon l'une quelconque des revendications 1 à 3, dans laquelle chaque injecteur de carburant de prémélange (32) est disposé entre le corps de buse (30) de la buse secondaire (18) et une buse primaire adjacente (16).
- Brûleur de turbine, comprenant le dispositif selon l'une quelconque des revendications 1 à 4,
la buse secondaire (18) comprenant en outre :- une source de carburant en communication fluidique avec la bride (22) ;- un premier tube de buse s'étendant depuis la bride (22) et en communication fluidique avec la source de carburant à travers la bride (22) ; et- au moins un tube d'injecteur ayant une extrémité proximale fixée à la bride (22) et s'étendant axialement le long d'une partie de la longueur du premier tube de buse, le tube d'injecteur étant fluidiquement connecté à la source de carburant à travers la bride (22) et séparé de la connexion entre la source de carburant et le premier tube de buse, et une extrémité distale espacée de l'extrémité proximale de la seconde buse. - Brûleur de turbine selon la revendication 5, dans lequel la buse secondaire (18) comprend en outre au moins un troisième tube s'étendant depuis la bride (22) et situé à l'intérieur du premier tube de buse, au moins un troisième tube étant connecté fluidiquement à une source de carburant pour alimenter sélectivement en carburant le brûleur.
- Brûleur de turbine selon la revendication 5, dans lequel les buses primaires (16) sont alignées radialement avec une pluralité de tubes d'injecteur, de sorte que chaque tube d'injecteur soit positionné entre une buse primaire (16) et le premier tube de buse situé centralement.
- Brûleur de turbine selon la revendication 7, dans lequel chaque tube d'injecteur a une section transversale généralement allongée.
- Brûleur de turbine selon la revendication 8, dans lequel la première extrémité de la section transversale allongée du tube d'injecteur est située à proximité du premier tube de buse et une seconde extrémité de la section transversale allongée est située à proximité d'une buse primaire (16).
- Brûleur de turbine selon la revendication 5, dans lequel au moins un injecteur comprend une pluralité de tubes d'injecteur agencés en un réseau annulaire autour du premier tube de buse.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL09004288T PL2216600T3 (pl) | 2009-02-04 | 2009-03-25 | Dysza palnika |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/365,539 US20100192582A1 (en) | 2009-02-04 | 2009-02-04 | Combustor nozzle |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2216600A2 EP2216600A2 (fr) | 2010-08-11 |
EP2216600A3 EP2216600A3 (fr) | 2010-09-01 |
EP2216600B1 true EP2216600B1 (fr) | 2018-12-26 |
Family
ID=40537866
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09004288.8A Active EP2216600B1 (fr) | 2009-02-04 | 2009-03-25 | Buse de brûleur |
Country Status (19)
Country | Link |
---|---|
US (2) | US20100192582A1 (fr) |
EP (1) | EP2216600B1 (fr) |
JP (2) | JP5199172B2 (fr) |
KR (1) | KR101117454B1 (fr) |
CN (1) | CN101793408B (fr) |
AR (1) | AR071511A1 (fr) |
AU (1) | AU2009201256B2 (fr) |
BR (1) | BRPI0901040A2 (fr) |
CA (1) | CA2660938C (fr) |
CL (1) | CL2009001002A1 (fr) |
DK (1) | DK2216600T3 (fr) |
HK (1) | HK1145866A1 (fr) |
HU (1) | HUE043933T2 (fr) |
IL (1) | IL198516A (fr) |
MX (1) | MX2009004300A (fr) |
MY (1) | MY148224A (fr) |
PL (1) | PL2216600T3 (fr) |
SG (1) | SG163465A1 (fr) |
TW (1) | TWI387682B (fr) |
Families Citing this family (55)
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US7870736B2 (en) * | 2006-06-01 | 2011-01-18 | Virginia Tech Intellectual Properties, Inc. | Premixing injector for gas turbine engines |
US20080268387A1 (en) * | 2007-04-26 | 2008-10-30 | Takeo Saito | Combustion equipment and burner combustion method |
US7908863B2 (en) * | 2008-02-12 | 2011-03-22 | General Electric Company | Fuel nozzle for a gas turbine engine and method for fabricating the same |
US9140454B2 (en) * | 2009-01-23 | 2015-09-22 | General Electric Company | Bundled multi-tube nozzle for a turbomachine |
US8539773B2 (en) * | 2009-02-04 | 2013-09-24 | General Electric Company | Premixed direct injection nozzle for highly reactive fuels |
EP2430362A1 (fr) * | 2009-05-07 | 2012-03-21 | General Electric Company | Injecteurs de carburant à plusieurs prémélangeurs |
US9354618B2 (en) | 2009-05-08 | 2016-05-31 | Gas Turbine Efficiency Sweden Ab | Automated tuning of multiple fuel gas turbine combustion systems |
US9671797B2 (en) | 2009-05-08 | 2017-06-06 | Gas Turbine Efficiency Sweden Ab | Optimization of gas turbine combustion systems low load performance on simple cycle and heat recovery steam generator applications |
US9267443B2 (en) | 2009-05-08 | 2016-02-23 | Gas Turbine Efficiency Sweden Ab | Automated tuning of gas turbine combustion systems |
US8437941B2 (en) | 2009-05-08 | 2013-05-07 | Gas Turbine Efficiency Sweden Ab | Automated tuning of gas turbine combustion systems |
US8959921B2 (en) * | 2010-07-13 | 2015-02-24 | General Electric Company | Flame tolerant secondary fuel nozzle |
EP2434222B1 (fr) * | 2010-09-24 | 2019-02-27 | Ansaldo Energia IP UK Limited | Méthode d'opération d'une chambre de combustion |
US8464537B2 (en) * | 2010-10-21 | 2013-06-18 | General Electric Company | Fuel nozzle for combustor |
US8899048B2 (en) | 2010-11-24 | 2014-12-02 | Delavan Inc. | Low calorific value fuel combustion systems for gas turbine engines |
US9003804B2 (en) | 2010-11-24 | 2015-04-14 | Delavan Inc | Multipoint injectors with auxiliary stage |
US8661825B2 (en) * | 2010-12-17 | 2014-03-04 | General Electric Company | Pegless secondary fuel nozzle including a unitary fuel injection manifold |
US8863525B2 (en) | 2011-01-03 | 2014-10-21 | General Electric Company | Combustor with fuel staggering for flame holding mitigation |
US20120308947A1 (en) * | 2011-06-06 | 2012-12-06 | General Electric Company | Combustor having a pressure feed |
US20130036743A1 (en) * | 2011-08-08 | 2013-02-14 | General Electric Company | Turbomachine combustor assembly |
US20130040254A1 (en) * | 2011-08-08 | 2013-02-14 | General Electric Company | System and method for monitoring a combustor |
EP2748533A4 (fr) * | 2011-08-22 | 2015-03-04 | Majed Toqan | Chambre de combustion annulaire tangentielle comprenant un prémélange d'air et de carburant destinée à être utilisée dans des moteurs à turbine à gaz |
US8850821B2 (en) * | 2011-10-07 | 2014-10-07 | General Electric Company | System for fuel injection in a fuel nozzle |
CN102367958A (zh) * | 2011-10-13 | 2012-03-07 | 四川长虹电器股份有限公司 | 一种高热负荷的燃气灶具 |
DE102011116317A1 (de) * | 2011-10-18 | 2013-04-18 | Rolls-Royce Deutschland Ltd & Co Kg | Magervormischbrenner eines Fluggasturbinentriebwerks |
US8997452B2 (en) | 2011-10-20 | 2015-04-07 | General Electric Company | Systems and methods for regulating fuel and reactive fluid supply in turbine engines |
US9134031B2 (en) | 2012-01-04 | 2015-09-15 | General Electric Company | Combustor of a turbomachine including multiple tubular radial pathways arranged at multiple circumferential and axial locations |
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AR071511A1 (es) | 2010-06-23 |
EP2216600A2 (fr) | 2010-08-11 |
PL2216600T3 (pl) | 2019-07-31 |
TWI387682B (zh) | 2013-03-01 |
BRPI0901040A2 (pt) | 2010-11-03 |
KR20100089722A (ko) | 2010-08-12 |
KR101117454B1 (ko) | 2012-03-02 |
AU2009201256A1 (en) | 2010-08-19 |
IL198516A0 (en) | 2010-02-17 |
US7707833B1 (en) | 2010-05-04 |
HK1145866A1 (en) | 2011-05-06 |
TW201030228A (en) | 2010-08-16 |
US20100192582A1 (en) | 2010-08-05 |
JP2012021765A (ja) | 2012-02-02 |
IL198516A (en) | 2012-01-31 |
MX2009004300A (es) | 2010-08-12 |
CN101793408B (zh) | 2012-10-03 |
JP2010181134A (ja) | 2010-08-19 |
CL2009001002A1 (es) | 2010-12-10 |
EP2216600A3 (fr) | 2010-09-01 |
CA2660938C (fr) | 2012-02-28 |
CN101793408A (zh) | 2010-08-04 |
JP5539938B2 (ja) | 2014-07-02 |
HUE043933T2 (hu) | 2019-09-30 |
MY148224A (en) | 2013-03-29 |
SG163465A1 (en) | 2010-08-30 |
CA2660938A1 (fr) | 2010-08-04 |
DK2216600T3 (en) | 2019-04-01 |
JP5199172B2 (ja) | 2013-05-15 |
AU2009201256B2 (en) | 2011-07-07 |
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